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Experimental aerothermodynamic research of hypersonic aircraftWind tunnel tests were conducted to establish a benchmark experimental data base for a genetic hypersonic aircraft vehicle. Comprehensive measurements were made at Mach 7 to give flow visualization, surface pressure, surface convective heat transfer, and flow field Pitot pressure for a delta platform all-body vehicle. The tests were conducted in the NASA/Ames 3.5-Foot Hypersonic Wind Tunnel at Reynolds numbers sufficient to give turbulent flow. Comparisons are made of the experimental results with computational solutions of the flow by an upwind parabolized Navier-Stokes code developed at Ames. Good agreement of experiment with solutions by the code is demonstrated.
Document ID
19900016638
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Cleary, Joseph W. (Eloret Corp. Palo Alto, CA, United States)
Date Acquired
September 6, 2013
Publication Date
August 23, 1990
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-186903
NAS 1.26:186903
Accession Number
90N25954
Funding Number(s)
CONTRACT_GRANT: NCC2-416
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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